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The heat for the anti icing system of a turbofan engine intake is provided by ? Aptitude > visibility

exemple question 151
Bleed air from hp compressor. In jet aeroplanes thermal anti ice system primarily supplied bleed air from engines (bleed air from hp compressor) the wing anti ice system has to protect leading edge or slats either partially or completely engine intake frontal area of elevator the vertical stabiliser.


The use of a hot air wing anti icing system ?

exemple question 152
The use of a hot air wing anti icing system Does not affect aerodynamic performance of wing causes a reduction in maximum thrust. In jet aeroplanes thermal anti ice system primarily supplied bleed air from engines (bleed air from hp compressor) the wing anti ice system has to protect leading edge or slats either partially or completely engine intake frontal area of elevator the vertical stabiliser since hot air tapped directly from a compressor stage temperature will rise in turbine which can limit thrust in order not to exceed maximum engine temperature.


Ice formation on turbofan engine intakes is usually ?

exemple question 153
Ice formation on turbofan engine intakes usually Prevented using compressor bleed air. In jet aeroplanes thermal anti ice system primarily supplied bleed air from engines (bleed air from hp compressor) the wing anti ice system has to protect leading edge or slats either partially or completely engine intake frontal area of elevator the vertical stabiliser since hot air tapped directly from a compressor stage temperature will rise in turbine which can limit thrust in order not to exceed maximum engine temperature.


exemple question 154
The ice protection propellers of modern turboprop aeroplanes works Prevented using compressor bleed air. ice formation on a propeller blade produces distortion to aerofoil section causing a loss in efficiency possible unbalance destructive vibration the build up of ice must be prevented there are two systems in use protection provided either an anti icing fluid system or an electrically powered thermal de icing system on modern turboprop (cessna caravan pilatus pc 12 beechcraft 90 to 1900d dash 8 atr 42/72 etc ) ice protection propellers works electrically in electrical systems basis effective de icing formed resistance wire heating elements bonded to leading edges of propeller blades in case of turbine engine propellers wire woven or sprayed elements are also bonded to front shell of spinner depending on type of aircraft power heating elements either direct current or alternating current is applied in a controlled sequence a cyclic timer unit in turbo propeller engine installations propeller heating circuit forms part of a power unit de icing anti icing system the cyclic control integrated with engine air intake heating circuit cessna 208 caravan.


exemple question 155
The heating facility the windshield of an aircraft Used on a continual basis as it reduces thermal gradients which adversely affect useful life of components. Howarthson the window heating system selected permanently on but heating elements are actually cycled on/off to maintain a constant temperature of window by keeping window warm not only keeps it clear of ice but increases its resistance to impact damage.


exemple question 156
The wing ice protection system currently used most large turboprop transport aeroplanes A pneumatic system with inflatable boots. On most turboprops this a de icing system (inflatable boots) .


exemple question 157
Electrically powered ice protection devices on aircraft are Used as anti icing devices pitot tubes static ports windshield. On most turboprops this a de icing system (inflatable boots) .


8
On most transport aircraft low pressure pumps of fuel system are Centrifugal pumps driven an electric motor. The pumps in question are pumps in fuel tanks they are known as 'lp pump also 'booster pump (less than 3 bars 40 psi) engine driven pumps would come under engine fuel system dividing line being made at low pressure cock or valve.


9
The fuel supply system on a jet engine includes a fuel heating device upstream of main fuel filter so as to Prevent at low fuel temperature risk of ice formation from water contained in fuel. The pumps in question are pumps in fuel tanks they are known as 'lp pump also 'booster pump (less than 3 bars 40 psi) engine driven pumps would come under engine fuel system dividing line being made at low pressure cock or valve.


10
On most transport jet aircraft low pressure pumps of fuel system are supplied with electric power of following type Prevent at low fuel temperature risk of ice formation from water contained in fuel. Fuel delivered under pressure from fuel pumps located in fuel tanks this 115 v ac powered fuel pumps are cooled lubricated fuel passing through pump notice fuel pump pressure should be supplied to engines at all times at high altitude without fuel pump pressure thrust deterioration or engine flameout may occur.


11
The pressure usually produced the booster pumps of fuel supply system of a large jet transport aeroplane within following range Prevent at low fuel temperature risk of ice formation from water contained in fuel. Fuel delivered under pressure from fuel pumps located in fuel tanks this 115 v ac powered fuel pumps are cooled lubricated fuel passing through pump notice fuel pump pressure should be supplied to engines at all times at high altitude without fuel pump pressure thrust deterioration or engine flameout may occur.


12
In a gas turbine engine lubrication system oil to fuel heat exchanger provides Oil cooling through thermal exchange with fuel. Fuel delivered under pressure from fuel pumps located in fuel tanks this 115 v ac powered fuel pumps are cooled lubricated fuel passing through pump notice fuel pump pressure should be supplied to engines at all times at high altitude without fuel pump pressure thrust deterioration or engine flameout may occur.


13
The fuel cross feed system Allows feeding of any engine from any fuel tank. The engine fuel manifolds are interconnected use of crossfeed valve fuel pressure can be provided from a any fuel tank with operating fuel pumps to both engines opening fuel crossfeed valve continued crossfeed can result in a progressive fuel imbalance.


14
The purpose of baffles in an aeroplane's integral fuel tank to Restrict fuel movements in tank. Baffles in a fuel tank are a series of partitions (wall) to control rapid flow of fuel prevent its sloshing these partitions have holes that allow fuel to feed to tank outlet but they keep fuel from surging enough to uncover fuel outlet.


15
On a transport type aircraft fuel tank system vented through Ram air scoops on underside of wing. This question refers to vent/pressurisation system used on b737 it a little misleading in that tank ventilation pressurisation systems are combined the ram air scoop on lower surface of leading edge delivers air at pressure to fuel tanks that pressure controlled at a few psi above atmospheric the vent system.


16
The types of fuel tanks used on most modern transport aircraft are Ram air scoops on underside of wing. This question refers to vent/pressurisation system used on b737 it a little misleading in that tank ventilation pressurisation systems are combined the ram air scoop on lower surface of leading edge delivers air at pressure to fuel tanks that pressure controlled at a few psi above atmospheric the vent system.


17
The pressurization of fuel tanks maintained The fuel vent system. Each tank vented to outside air in order to maintain atmospheric pressure within tank air vents are designed to minimize possibility of their stoppage dirt ice formation in order to permit rapid changes in internal air pressure size of vent proportional to size of tank thus preventing collapse of tank in a steep dive or glide.


18
On a jet aircraft fuel heaters are The fuel vent system. Each tank vented to outside air in order to maintain atmospheric pressure within tank air vents are designed to minimize possibility of their stoppage dirt ice formation in order to permit rapid changes in internal air pressure size of vent proportional to size of tank thus preventing collapse of tank in a steep dive or glide.


19
The automatic fuelling shut off valve Stops fuelling as soon as a certain fuel level reached inside tank. Each tank vented to outside air in order to maintain atmospheric pressure within tank air vents are designed to minimize possibility of their stoppage dirt ice formation in order to permit rapid changes in internal air pressure size of vent proportional to size of tank thus preventing collapse of tank in a steep dive or glide.


20
During re fuelling automatic shut off valves will switch off fuel supply system when The fuel has reached a predetermined volume or mass. Each tank vented to outside air in order to maintain atmospheric pressure within tank air vents are designed to minimize possibility of their stoppage dirt ice formation in order to permit rapid changes in internal air pressure size of vent proportional to size of tank thus preventing collapse of tank in a steep dive or glide.



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